CN113847146A - Shaft power output unit body based on pneumatic and structural matching design - Google Patents
Shaft power output unit body based on pneumatic and structural matching design Download PDFInfo
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- CN113847146A CN113847146A CN202111009851.9A CN202111009851A CN113847146A CN 113847146 A CN113847146 A CN 113847146A CN 202111009851 A CN202111009851 A CN 202111009851A CN 113847146 A CN113847146 A CN 113847146A
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- output unit
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
- F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Rolling Contact Bearings (AREA)
- Support Of The Bearing (AREA)
Abstract
The invention discloses a shaft power output unit body based on pneumatic and structure matching design, which relates to the technical field of turboprop engines and solves the technical problems of more parts and complex installation of the conventional shaft power output unit body; according to the invention, the shaft sleeve and the lubricating oil loop are integrally designed, and the integral front-section tail nozzle is tightly sealed through the labyrinth, so that the output power is realized, and the number of parts is reduced as much as possible, thereby simplifying the installation steps and the structure of an engine.
Description
Technical Field
The invention relates to the technical field of turboprop engines, in particular to the technical field of power turbine type shaft power output unit bodies.
Background
The shaft power output unit body is positioned at the rear part of the fuel gas generator and in front of the speed reducer, and the unit body enables high-temperature and high-pressure fuel gas generated by the fuel gas generator to expand in the power turbine to push the power turbine to rotate to output work. The shaft connected with the turbine is the same as the input shaft of the speed reducer, so that the shaft drives the speed reducer to work in the rotating process, and the propeller behind the speed reducer is driven to work. At the same time, the unit body also acts as a transmission force because the rear reducer is relatively heavy. The existing shaft power output unit body is mainly divided into a power turbine, an input shaft, a shafting support and a gas flow passage, and under the limitation of the compact size of a turboprop engine, the existing shaft power output unit body has more parts, is complex to install and has the relative precision requirement which is not easy to meet.
Therefore, in order to solve the above problems, an axial power output unit body with integrated design of partial functional parts is urgently needed.
Disclosure of Invention
The invention aims to: in order to solve the technical problems, the invention provides an axial power output unit body designed based on pneumatic and structural matching.
The invention specifically adopts the following technical scheme for realizing the purpose:
the utility model provides an axle power output cell cube based on pneumatics and structural matching nature design, which comprises a rotating shaft, from left to right be equipped with reverse nut in proper order in the pivot, power turbine, the integral type anterior segment jet nozzle that has the labyrinth, back end jet nozzle, the back end casing of holding back end jet nozzle, lock nut, be equipped with the axle sleeve of being connected with integral type anterior segment jet nozzle in the pivot, be equipped with the stabilising arrangement with lock nut contact between axle sleeve and the pivot, be equipped with the lubricating oil return circuit with stabilising arrangement intercommunication on the axle sleeve, integral type anterior segment jet nozzle, back end casing constitutes the air current chamber way.
The integral type anterior segment jet nozzle is equipped with tail nozzle cover, gusset, support section from inside to outside in proper order, and the inner wall of support section is equipped with a plurality of and evenly distributed at its self gusset, and the inner wall of tail nozzle cover is equipped with the broach.
The rotating shaft is provided with a lining, the tail nozzle is sleeved on the lining, and the comb teeth are contacted with the outer wall of the lining.
The bush includes fixed cover, the solid fixed ring that sets gradually from left to right, and solid fixed ring's external diameter is greater than the external diameter of fixed cover, and solid fixed ring forms the fixed slot with the pivot, is equipped with anterior angle contact ceramic ball bearing in the fixed slot, and the extension end and the power turbine contact of fixed cover.
The tail nozzle sleeve inner wall is equipped with the holding chamber, and tail nozzle sleeve outer wall is equipped with the spread groove, and solid fixed ring extends to the holding intracavity, and the holding intracavity is equipped with the cushion, and solid fixed ring is established in the cushion, and anterior angle contact ceramic ball bearing establishes at the holding intracavity, and anterior angle contact ceramic ball bearing top is equipped with can dismantle the axle sleeve of being connected with holding chamber wall, and the extension end and the cushion contact of axle sleeve are equipped with the back end tail nozzle of dismantling the connection on the spread groove.
The link of supporting the section is connected with the anterior segment casing, is equipped with a plurality of and evenly distributed on its self mounting hole on the anterior segment casing, supports the section holding in the anterior segment casing.
The stabilizing device comprises a front angle contact ceramic ball bearing, a front stop block, a shaft system stop block and a rear stop block which are sequentially arranged in an inner cavity of the shaft sleeve from left to right, a pre-tightening spring wound on a rotating shaft is arranged in the shaft system stop block, and a rear angle contact ceramic ball bearing is arranged between the rear stop block and a locking nut.
The lubricating oil loop comprises a lubricating oil inlet channel and a lubricating oil outlet channel which are arranged on the shaft sleeve, the front stop block is sequentially provided with an oil inlet communicated with the lubricating oil inlet channel and an oil outlet communicated with the lubricating oil outlet channel from top to bottom, and the oil inlet and the oil outlet are communicated with the front corner contact ceramic ball bearing.
Two exhaust ports which are symmetrically arranged along the vertical central line of the rear section shell are arranged on the rear section shell.
The extending end of the rotating shaft is provided with a key slot.
The invention has the following beneficial effects:
1. in the invention, the shaft sleeve and the lubricating oil loop are integrally designed and the integrated front-section tail nozzle is tightly sealed through the labyrinth, so that the damage of the bearing due to overheating caused by the fact that a large amount of high-temperature gas invades into a bearing cavity through a gap can be prevented, and a support can be provided for a flow guide wall for guiding the high-temperature gas, therefore, the invention can reduce the number of parts as much as possible and simplify the structure of an engine while realizing the output power.
2. In the invention, the lubricating oil loop arranged on the shaft sleeve can cool the front-angle contact ceramic ball bearing, thereby further reducing the temperature of the front-angle contact ceramic ball bearing in the using process.
3. In the invention, the integrated front-section tail nozzle, the rear-section tail nozzle and the rear-section shell form an airflow cavity channel, wherein the integrated front-section tail nozzle provides flow guide for high-temperature gas, so that the high-temperature gas can flow in the airflow cavity channel and finally flow out of the rear-section shell, and the integrated front-section tail nozzle, the rear-section tail nozzle and the rear-section shell form an intermediate force bearing structure of the engine.
4. According to the invention, the grate is arranged on the inner wall of the tail nozzle sleeve, so that the bearing can be prevented from being damaged due to overheating caused by the fact that a large amount of high-temperature natural gas enters the bearing cavity through gaps, and the tail nozzle sleeve is connected with the supporting section through the uniformly distributed rib plates, so that the distance between the rib plates provides a flow guide channel for the high-temperature natural gas.
5. According to the invention, the bushing is arranged on the rotating shaft, so that the contact between the grate and the bushing is tighter, and a large amount of high-temperature natural gas is prevented from invading into the bearing cavity through the gap.
6. In the invention, because the outer diameter of the fixing ring is larger than that of the fixing sleeve, the fixing ring can prevent a large amount of high-temperature natural gas from invading into the bearing cavity through a gap, and can form a fixed front angle with the rotating shaft to contact the ceramic ball bearing.
7. In the invention, the shaft sleeve and the rear-section tail nozzle are respectively detachably connected with the tail nozzle sleeve, so that the connectivity of the shaft sleeve, the rear-section tail nozzle and the tail nozzle sleeve can be ensured, and the influence of the shaft sleeve and the rear-section tail nozzle on the airflow of high-temperature natural gas is reduced.
8. According to the invention, the cushion block can enable the installation of the shaft sleeve, the front corner contact ceramic ball bearing and the bush to be more compact and closed, so that a large amount of high-temperature natural gas is prevented from invading into a bearing cavity through a gap.
9. In the invention, the mounting hole on the front section shell can facilitate the installation of the front section shell and the gas generator by workers.
10. According to the invention, the pre-tightening springs can provide pre-tightening force for the front angle contact ceramic ball bearings and the rear angle contact ceramic ball bearings at the left end and the right end of the rotating shaft, so that the stability of the whole shafting is ensured in the use process of the engine, and the vibration is reduced.
11. In the invention, the lubricating oil enters the front-angle contact ceramic ball bearing from the lubricating oil inlet channel and the oil inlet in sequence, and the front-angle contact ceramic ball bearing is communicated with the oil inlet and the oil outlet, so the lubricating oil is discharged from the oil outlet and the lubricating oil outlet channel in sequence after being cooled for the front-angle contact ceramic ball bearing, and the bearing is prevented from being damaged due to overheating caused by the fact that a large amount of high-temperature natural gas enters the bearing cavity through the gap due to the integrated design of the shaft sleeve, the lubricating oil inlet channel and the lubricating oil outlet channel, and the number of parts is also reduced.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1;
FIG. 3 is a schematic structural view of an integral forward nozzle;
FIG. 4 is a schematic structural view of a support section;
FIG. 5 is a schematic view of a structure of a fixing groove;
FIG. 6 is a schematic view of the linkage of the front shell, the rear shell, and the rear jet nozzle;
FIG. 7 is a schematic illustration of the construction of the aft nozzle;
reference numerals: 11 rotating shaft, 111 key groove, 112 fixed groove, 12 shaft sleeve, 121 lubricating oil inlet, 122 lubricating oil outlet, 123 oil outlet, 124 oil inlet, 13 rear block, 14 shafting block, 141 spring, 15 front block, 16 front corner contact ceramic ball bearing, 17 cushion block, 18 bushing, 181 fixed sleeve, 182 fixed ring, 19 integral front section tail nozzle, 191 tail nozzle sleeve, 1911 accommodating cavity, 1912 connecting groove, 192 labyrinth, 193 gusset, 194 supporting section, 20 power turbine, 21 reverse nut, 22 front section shell, 221 mounting hole, 23 rear section tail nozzle, 24 rear section shell, 241 exhaust port, 25 rear corner contact ceramic ball bearing, 26 lock nut.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
As shown in fig. 1 to 7, the present embodiment provides a shaft power output unit based on pneumatic and structural matching design, which includes a rotating shaft 11, a reverse nut 21, a power turbine 20, an integrated front nozzle 19 with a comb 192, a rear nozzle 23, a rear casing 24 for accommodating the rear nozzle 23, and a lock nut 26 are sequentially disposed on the rotating shaft 11 from left to right, a shaft sleeve 12 connected to the integrated front nozzle 19 is disposed on the rotating shaft 11, a stabilizing device contacting with the lock nut 26 is disposed between the shaft sleeve 12 and the rotating shaft 11, a lubricating oil loop communicated with the stabilizing device is disposed on the shaft sleeve 12, and the integrated front nozzle 19, the rear nozzle 23, and the rear casing 24 form an air flow channel.
In the embodiment, the shaft sleeve 12 and the lubricating oil loop are designed integrally, and the integral front-section tail nozzle 19 is sealed through the labyrinth 192, so that the output power is realized, and the number of parts is reduced as much as possible, thereby simplifying the installation steps and the structure of the engine; the oil circuit arranged on the shaft sleeve 12 can cool the front-angle contact ceramic ball bearing 16, so that the temperature of the front-angle contact ceramic ball bearing 16 in the use process is further reduced, the damage of the angular contact ceramic ball bearing due to overheating is avoided, the integrated front-section tail nozzle 19 with the grid teeth 192 can prevent a large amount of high-temperature natural gas from invading into a bearing cavity through gaps to cause the damage of the bearing due to overheating, and the integrated front-section tail nozzle 19, the rear-section tail nozzle 23 and the rear-section shell 24 form an airflow cavity channel, so that a flow channel is provided for high-temperature fuel oil, and an intermediate bearing structure of an engine is formed; because the lubricating oil loop is arranged on the shaft sleeve 12, the integrated front section tail nozzle 19, the rear section tail nozzle 23 and the rear section shell 24 form an air flow cavity channel and also form an intermediate bearing structure of the engine, the embodiment realizes output power, reduces the number of parts as much as possible and simplifies the structure of the engine.
Specifically, the high-temperature gas passes through the power turbine 20, flows through an airflow channel formed by the integrated front-section tail nozzle 19, the rear-section tail nozzle 23, the front-section shell 22 and the rear-section shell 24 which are sealed by the labyrinth 192, and is finally discharged from the rear-section shell 24. The power turbine 20 converts the energy of the high-temperature gas into mechanical work by driving the rotation of the rotating shaft 11, and the rear section of the rotating shaft 11 is connected with the speed reducer, so that the purposes of driving an external load and outputting power are achieved.
Example 2
As shown in fig. 1 to 4, on the basis of the first embodiment, the integrated front-section jet nozzle 19 provided by the present embodiment is sequentially provided with a jet nozzle sleeve 191, rib plates 193, and a support section 194 from inside to outside, the inner wall of the support section 194 is provided with a plurality of rib plates 193 uniformly distributed on the inner wall, and the inner wall of the jet nozzle sleeve 191 is provided with grate teeth 192.
Furthermore, a bushing 18 is arranged on the rotating shaft 11, a tail nozzle sleeve 191 is sleeved on the bushing 18, and the comb teeth 192 are in contact with the outer wall of the bushing 18.
Further, the bushing 18 includes a fixing sleeve 181 and a fixing ring 182 sequentially arranged from left to right, an outer diameter of the fixing ring 182 is larger than an outer diameter of the fixing sleeve 181, the fixing ring 182 and the rotating shaft 11 form a fixing groove 112, a front corner contact ceramic ball bearing 16 is arranged in the fixing groove 112, and an extending end of the fixing sleeve 181 contacts the power turbine 20.
Further, the inner wall of the tail nozzle sleeve 191 is provided with an accommodating cavity 1911, the outer wall of the tail nozzle sleeve 191 is provided with a connecting groove 1912, the fixing ring 182 extends into the accommodating cavity 1911, a cushion block 17 is arranged in the accommodating cavity 1911, the fixing ring 182 is arranged in the cushion block 17, the front corner contact ceramic ball bearing 16 is arranged in the accommodating cavity 1911, a shaft sleeve 12 detachably connected with the cavity wall of the accommodating cavity 1911 is arranged above the front corner contact ceramic ball bearing 16, the extending end of the shaft sleeve 12 is in contact with the cushion block 17, and the connecting groove 1912 is provided with a rear-end tail nozzle 23 detachably connected.
In the embodiment, the bushing 18 is arranged on the rotating shaft 11, and the bushing 18 is in contact with the comb 192, so that a large amount of high-temperature natural gas can be prevented from entering the bearing cavity through gaps, because the tail nozzle sleeve 191 is connected with the support section 194 through the plurality of uniformly distributed rib plates 193, the distance between the plurality of rib plates 193 provides a flow guide channel for the high-temperature natural gas, and because the outer diameter of the fixing ring 182 is larger than that of the fixing sleeve 181, the fixing ring 182 can form a fixed front angle with the rotating shaft 11 to be in contact with the fixing groove 112 of the ceramic ball bearing 16; the inner wall of the tail nozzle sleeve 191 is provided with a containing cavity 1911, the outer wall is provided with a connecting groove 1912, the containing cavity is used for connecting the shaft sleeve 12 and the rear tail nozzle, the influence of the high-temperature natural gas on the airflow is reduced, the cushion block 17 can enable the installation of the shaft sleeve 12, the front corner contact ceramic ball bearing 16 and the lining 18 to be more compact and closed, and therefore a large amount of high-temperature natural gas is prevented from entering the bearing cavity through gaps.
Specifically, the rear-stage jet nozzle 23 and the shaft sleeve 12 are connected to the jet nozzle head cover 191 by bolts.
Example 3
As shown in fig. 1 to 7, on the basis of the second embodiment, the connection end of the supporting section 194 is connected to the front section housing 22, a plurality of mounting holes 221 are uniformly distributed on the front section housing 22, and the supporting section 194 is accommodated in the front section housing 22.
In the embodiment, the front casing 22, the integrated front jet nozzle 19, the rear jet nozzle 23 and the rear casing 24 form a complete cavity, and the support section 194 is disposed in the front casing 22, so that the front casing 22 provides a passage for the high temperature natural gas to flow to the power turbine 20; mounting holes 221 in the front housing 22 facilitate installation of the front housing 22 and the gasifier by personnel.
Example 4
As shown in fig. 1, on the basis of the first embodiment, the stabilizing device provided in this embodiment includes a front corner contact ceramic ball bearing 16, a front stop block 15, a shafting stop block 14, and a rear stop block 13, which are sequentially disposed in an inner cavity of a shaft sleeve 12 from left to right, a pre-tightening spring 141 wound on a rotating shaft 11 is disposed in the shafting stop block 14, and a rear corner contact ceramic ball bearing 25 is disposed between the rear stop block 13 and a lock nut 26.
Further, the lubricating oil loop comprises a lubricating oil inlet 121 channel and a lubricating oil outlet 122 channel which are arranged on the shaft sleeve 12, the front stop block 15 is sequentially provided with an oil inlet 124 communicated with the lubricating oil inlet 121 channel and an oil outlet 123 communicated with the lubricating oil outlet 122 channel from top to bottom, and the oil inlet 124 and the oil outlet 123 are communicated with the front corner contact ceramic ball bearing 16.
In this embodiment, the pre-tightening spring 141 can provide pre-tightening force for the front angle contact ceramic ball bearing 16 and the rear angle contact ceramic ball bearing 25 at the left end and the right end of the rotating shaft 11, so as to ensure the stability of the whole shaft system and reduce vibration in the use process of the engine, and the front stop block 15 and the rear stop block 13 can be used for fixing the shaft system stop block 14; the lubricating oil enters the front-angle contact ceramic ball bearing 16 from the lubricating oil inlet 121 channel and the oil inlet 124 in sequence, and as the shaft cavity of the front-angle contact ceramic ball bearing 16 is communicated with the oil inlet 124 and the oil outlet 123, the lubricating oil is discharged from the oil outlet 123 and the lubricating oil outlet 122 channel after cooling the front-angle contact ceramic ball bearing 16, therefore, the shaft sleeve 12, the lubricating oil inlet 121 channel and the lubricating oil outlet 122 channel are integrally designed, so that a large amount of high-temperature natural gas can be prevented from invading the bearing cavity through gaps to cause overheating and damage of the bearing, and the number of parts is reduced.
Example 5
As shown in fig. 6, on the basis of the first embodiment, the present embodiment provides that two exhaust ports 241 are symmetrically arranged along the vertical center line of the rear-section shell 24; the extended end of the rotating shaft 11 is provided with a key groove 111.
In the embodiment, after the high-temperature natural gas passes through the airflow channel formed by the integrated front-section tail nozzle 19, the rear-section tail nozzle 23 and the rear-section shell 24, the high-temperature natural gas is finally discharged from the exhaust port 241 of the rear-section shell 24, so that the purpose of compact high-power-density turboshaft engine power output is achieved; the extension end of the rotating shaft 11 is provided with a key groove 111, so that a worker can conveniently fix the speed reducer, and the locking nut 26 can be taken down during installation, so that the rear-angle contact ceramic ball bearing 25 is tightly jacked by the front shell of the speed reducer, and integration is realized.
Claims (10)
1. The utility model provides a shaft power output cell cube based on pneumatics and structural matching nature design, includes pivot (11), its characterized in that, rear shell (24), lock nut (26) that pivot (11) were equipped with reverse nut (21), power turbine (20), integral type front segment tail nozzle (19) that have comb tooth (192), rear segment tail nozzle (23), holding rear segment tail nozzle (23) from left to right in proper order, be equipped with axle sleeve (12) of being connected with integral type front segment tail nozzle (19) in pivot (11), be equipped with the stabilising arrangement who contacts with lock nut (26) between axle sleeve (12) and pivot (11), be equipped with the lubricating oil return circuit with stabilising arrangement intercommunication on axle sleeve (12), integral type front segment tail nozzle (19), rear segment tail nozzle (23), rear shell (24) constitute the air current chamber way.
2. The shaft power output unit body based on aerodynamic design and structural matching design according to claim 1, characterized in that the integrated front section jet nozzle (19) is sequentially provided with a jet nozzle sleeve (191), rib plates (193) and a support section (194) from inside to outside, the inner wall of the support section (194) is provided with a plurality of rib plates (193) which are uniformly distributed on the support section, and the inner wall of the jet nozzle sleeve (191) is provided with a comb tooth (192).
3. The shaft power output unit body designed based on the pneumatic and structural matching property as claimed in claim 2, wherein a bushing (18) is arranged on the rotating shaft (11), the tail nozzle sleeve (191) is sleeved on the bushing (18), and the comb teeth (192) are in contact with the outer wall of the bushing (18).
4. The shaft power output unit body designed based on the aerodynamic performance and the structural matching performance as claimed in claim 3, wherein the bushing (18) comprises a fixed sleeve (181) and a fixed ring (182) which are sequentially arranged from left to right, the outer diameter of the fixed ring (182) is larger than that of the fixed sleeve (181), the fixed ring (182) and the rotating shaft (11) form a fixed groove (112), a front corner contact ceramic ball bearing (16) is arranged in the fixed groove (112), and the extending end of the fixed sleeve (181) is in contact with the power turbine (20).
5. The shaft power output unit body designed based on the pneumatic and structural matching performance of claim 4 is characterized in that an accommodating cavity (1911) is formed in the inner wall of the tail nozzle sleeve (191), a connecting groove (1912) is formed in the outer wall of the tail nozzle sleeve (191), the fixing ring (182) extends into the accommodating cavity (1911), a cushion block (17) is arranged in the accommodating cavity (1911), the fixing ring (182) is arranged in the cushion block (17), the front-angle contact ceramic ball bearing (16) is arranged in the accommodating cavity (1911), a shaft sleeve (12) detachably connected with the wall of the accommodating cavity (1911) is arranged above the front-angle contact ceramic ball bearing (16), the extending end of the shaft sleeve (12) is in contact with the cushion block (17), and a rear-section tail nozzle (23) detachably connected with the connecting groove (1912) is arranged on the connecting groove.
6. The shaft power output unit body designed based on the pneumatic and structural matching property as claimed in claim 2, wherein the connecting end of the supporting section (194) is connected with a front section shell (22), a plurality of mounting holes (221) are formed in the front section shell (22) and are uniformly distributed in the front section shell, and the supporting section (194) is accommodated in the front section shell (22).
7. The shaft power output unit body designed based on the pneumatic and structural matching is characterized in that the stabilizing device comprises a front corner contact ceramic ball bearing (16), a front stop block (15), a shaft system stop block (14) and a rear stop block (13) which are sequentially arranged in an inner cavity of a shaft sleeve (12) from left to right, a pre-tightening spring (141) wound on a rotating shaft (11) is arranged in the shaft system stop block (14), and a rear corner contact ceramic ball bearing (25) is arranged between the rear stop block (13) and a locking nut (26).
8. The shaft power output unit body designed based on the pneumatic and structural matching performance is characterized in that the lubricating oil loop comprises a lubricating oil inlet (121) channel and a lubricating oil outlet (122) channel which are arranged on the shaft sleeve (12), the front stop block (15) is sequentially provided with an oil inlet (124) communicated with the lubricating oil inlet (121) channel and an oil outlet (123) communicated with the lubricating oil outlet (122) channel from top to bottom, and the oil inlet (124) and the oil outlet (123) are communicated with the front corner contact ceramic ball bearing (16).
9. The shaft power output unit body designed based on the pneumatic and structural matching of claim 1, characterized in that the rear section shell (24) is provided with two air outlets (241) symmetrically arranged along its own vertical center line.
10. Shaft power output unit body based on aerodynamic and structural matching design according to claim 1, characterized in that the extended end of the rotating shaft (11) is provided with a key slot (111).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111009851.9A CN113847146B (en) | 2021-08-30 | 2021-08-30 | Shaft power output unit body based on pneumatic and structural matching design |
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| CN202111009851.9A CN113847146B (en) | 2021-08-30 | 2021-08-30 | Shaft power output unit body based on pneumatic and structural matching design |
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| CN113847146B CN113847146B (en) | 2022-08-30 |
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| US20120177493A1 (en) * | 2009-09-18 | 2012-07-12 | Snecma | Turbine engine with contra-rotating non-ducted propellers |
| US20190118934A1 (en) * | 2017-10-24 | 2019-04-25 | Safran Transmission Systems | Oil transfer for a control system regulating the propeller pitch of a turbine engine |
| CN108798904A (en) * | 2018-04-28 | 2018-11-13 | 上海啸风航空科技有限公司 | A kind of novel microminiature whirlpool paddle jet engine |
| CN213063765U (en) * | 2020-08-21 | 2021-04-27 | 尹喜连 | Double-propeller coaxial turboshaft engine |
| CN213928580U (en) * | 2020-08-21 | 2021-08-10 | 尹喜连 | Turboprop engine for vertical take-off and landing aircraft |
| CN113062798A (en) * | 2021-04-19 | 2021-07-02 | 中国航发湖南动力机械研究所 | Gas turbine rotor and turbine structure of rear output type turboprop engine |
| CN113006940A (en) * | 2021-05-06 | 2021-06-22 | 中国航发湖南动力机械研究所 | Micro turboprop engine without external speed reducer |
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